| Patent application number | Description | Published |
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| 20080264033 | METHODS AND SYSTEMS TO FACILITATE REDUCING NOx EMISSIONS IN COMBUSTION SYSTEMS - A method for assembling a gas turbine combustor system is provided. The method includes providing a combustion liner including a center axis, an outer wall, a first end, and a second end. The outer wall is orientated substantially parallel to the center axis. The method also includes coupling a transition piece to the liner second end. The transition piece includes an outer wall. The method further includes coupling a plurality of lean-direct injectors along at least one of the liner outer wall and the transition piece outer wall such that the injectors are spaced axially apart along the wall. | 10-30-2008 |
| 20080267783 | METHODS AND SYSTEMS TO FACILITATE OPERATING WITHIN FLAME-HOLDING MARGIN - A method to facilitate controlling flame-holding margins in a turbine engine is provided. The method includes coupling at least one turbine nozzle segment within the turbine engine, wherein the at least one turbine nozzle segment includes at least one vane extending between an inner band and an outer band. The method also includes positioning at least one fuel injection orifice in a surface of the at least one vane, channeling a fuel through the at least one fuel injection orifice into a compressed fluid flow to establish a jet penetration height, and defining an operating window by adjusting an operating parameter of the fuel to reduce the jet penetration height and to facilitate reducing the flame-holding margins. | 10-30-2008 |
| 20090139236 | PREMIXING DEVICE FOR ENHANCED FLAMEHOLDING AND FLASH BACK RESISTANCE - A premixing device is provided. The premixing device includes a fuel inlet configured to introduce a fuel within the premixing device and an air inlet configured to introduce air within the premixing device. The premixing device also includes a plurality of swirler vanes configured to provide a swirl movement to the fuel and/or air to facilitate mixing of the fuel and air to form a gaseous pre-mix, wherein a shape of each of the plurality of swirler vanes is selected to control an axial velocity profile of the fuel and/or air within the premixing device. | 06-04-2009 |
| 20090314000 | COANDA PILOT NOZZLE FOR LOW EMISSION COMBUSTORS - A low emission combustor includes a combustor housing defining a combustion chamber. A secondary nozzle is disposed along a centerline of the combustion chamber and configured to inject air or a first mixture of air and fuel on a downstream side of the combustion chamber. The secondary nozzle includes an air inlet configured to introduce a first fluid including air, a diluent, or combinations thereof into the secondary nozzle. At least one fuel plenum is configured to introduce a second fluid including a fuel, another diluent, or combinations thereof into the secondary nozzle and over a predetermined profile proximate to the fuel plenum. The predetermined profile is configured to facilitate attachment of the second fluid to the profile to form a fluid boundary layer and to entrain incoming first fluid through the fluid boundary layer to promote mixing of the first fluid and the second fluid and fuel to produce the first fluid. A plurality of primary fuel nozzles are disposed proximate on an upstream side of the combustion chamber and located around the secondary nozzle and configured to inject air or a second mixture of air and fuel to an upstream side of the combustion chamber. | 12-24-2009 |
| 20090320484 | METHODS AND SYSTEMS TO FACILITATE REDUCING FLASHBACK/FLAME HOLDING IN COMBUSTION SYSTEMS - A method for assembling a premixing injector is provided. The method includes providing a centerbody including a center axis and a radially outer surface, and providing an inlet flow conditioner. The inlet flow conditioner includes a radially outer wall, a radially inner wall, and an end wall coupled substantially perpendicularly between the outer wall and the inner wall. Each of the outer wall and the end wall include a plurality of openings defined therein. The outer wall, the inner wall, and the end wall define a first passage therebetween. The method also includes coupling the inlet flow conditioner to the centerbody such that the inlet flow conditioner substantially circumscribes the centerbody, such that the inner wall is substantially parallel to the centerbody outer surface, and such that a second passage is defined between the centerbody outer surface and the inner wall. | 12-31-2009 |
| 20100008179 | PRE-MIXING APPARATUS FOR A TURBINE ENGINE - A pre-mixing apparatus for a turbine engine includes a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish at least one fluid delivery plenum, and a plurality of fluid delivery tubes extending through at least a portion of the at least one fluid delivery plenum. Each of the plurality of fluid delivery tubes includes at least one fluid delivery opening fluidly connected to the at least one fluid delivery plenum. With this arrangement, a first fluid is selectively delivered to the at least one fluid delivery plenum, passed through the at least one fluid delivery opening and mixed with a second fluid flowing through the plurality of fluid delivery tubes prior to being combusted in a combustion chamber of a turbine engine. | 01-14-2010 |
| 20100011771 | COANDA INJECTION SYSTEM FOR AXIALLY STAGED LOW EMISSION COMBUSTORS - The low emission combustor includes a combustor housing defining a combustion chamber having a plurality of combustion zones. A liner sleeve is disposed in the combustion housing with a gap formed between the liner sleeve and the combustor housing. A secondary nozzle is disposed along a centerline of the combustion chamber and configured to inject a first fluid comprising air, at least one diluent, fuel, or combinations thereof to a downstream side of a first combustion zone among the plurality of combustion zones. A plurality of primary fuel nozzles is disposed proximate to an upstream side of the combustion chamber and located around the secondary nozzle and configured to inject a second fluid comprising air and fuel to an upstream side of the first combustion zone. The combustor also includes a plurality of tertiary coanda nozzles. Each tertiary coanda nozzle is coupled to a respective dilution hole. The tertiary coanda nozzles are configured to inject a third fluid comprising air, at least one other diluent, fuel, or combinations thereof to one or more remaining combustion zones among the plurality of combustion zones. | 01-21-2010 |
| 20100084490 | Premixed Direct Injection Nozzle - An injection nozzle having a main body portion with an outer peripheral wall is disclosed. The nozzle includes a plurality of fuel/air mixing tubes disposed within the main body portion and a fuel flow passage fluidly connected to the plurality of fuel/air mixing tubes. Fuel and air are partially premixed inside the plurality of the tubes. A second body portion, having an outer peripheral wall extending between a first end and an opposite second end, is connected to the main body portion. The partially premixed fuel and air mixture from the first body portion gets further mixed inside the second body portion. The second body portion converges from the first end toward said second end. The second body portion also includes cooling passages that extend along all the walls around the second body to provide thermal damage resistance for occasional flame flash back into the second body. | 04-08-2010 |
| 20100089367 | FUEL NOZZLE ASSEMBLY - A fuel nozzle assembly is provided. The assembly includes an outer nozzle body having a first end and a second end and at least one inner nozzle tube having a first end and a second end. One of the nozzle body or nozzle tube includes a fuel plenum and a fuel passage extending therefrom, while the other of the nozzle body or nozzle tube includes a fuel injection hole slidably aligned with the fuel passage to form a fuel flow path therebetween at an interface between the body and the tube. The nozzle body and the nozzle tube are fixed against relative movement at the first ends of the nozzle body and nozzle tube, enabling the fuel flow path to close at the interface due to thermal growth after a flame enters the nozzle tube. | 04-15-2010 |
| 20100139280 | MULTI-TUBE THERMAL FUSE FOR NOZZLE PROTECTION FROM A FLAME HOLDING OR FLASHBACK EVENT - A protection system for a pre-mixing apparatus for a turbine engine, includes: a main body having an inlet portion, an outlet portion and an exterior wall that collectively establish a fuel delivery plenum; and a plurality of fuel mixing tubes that extend through at least a portion of the fuel delivery plenum, each of the plurality of fuel mixing tubes including at least one fuel feed opening fluidly connected to the fuel delivery plenum; at least one thermal fuse disposed on an exterior surface of at least one tube, the at least one thermal fuse including a material that will melt upon ignition of fuel within the at least one tube and cause a diversion of fuel from the fuel feed opening to at least one bypass opening. A method and a turbine engine in accordance with the protection system are also provided. | 06-10-2010 |
| 20100180600 | NOZZLE FOR A TURBOMACHINE - A turbomachine includes a compressor, a combustor operatively connected to the compressor, and an injection nozzle operatively connected to the combustor. The injection nozzle includes a main body having a first end section that extends to a second end section to define an inner flow path. The injection nozzle further includes an outlet arranged at the second end section of the main body, at least one passage that extends within the main body and is fluidly connected to the outlet, and at least one conduit extending between the inner flow path and the at least one passage. | 07-22-2010 |
| 20100186413 | BUNDLED MULTI-TUBE NOZZLE FOR A TURBOMACHINE - A turbomachine includes a compressor, a combustor operatively connected to the compressor, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a cap member having a first surface that extends to a second surface. The cap member further includes a plurality of openings. A plurality of bundled mini-tube assemblies are detachably mounted in the plurality of openings in the cap member. Each of the plurality of bundled mini-tube assemblies includes a main body section having a first end section and a second end section. A fluid plenum is arranged within the main body section. A plurality of tubes extend between the first and second end sections. Each of the plurality of tubes is fluidly connected to the fluid plenum. | 07-29-2010 |
| 20100192581 | PREMIXED DIRECT INJECTION NOZZLE - A fuel/air mixing tube for use in a fuel/air mixing tube bundle is provided. The fuel/air mixing tube includes an outer tube wall extending axially along a tube axis between an inlet end and an exit end, the outer tube wall having a thickness extending between an inner tube surface having a inner diameter and an outer tube surface having an outer tube diameter. The tube further includes at least one fuel injection hole having a fuel injection hole diameter extending through the outer tube wall, the fuel injection hole having an injection angle relative to the tube axis. The invention provides good fuel air mixing with low combustion generated NOx and low flow pressure loss translating to a high gas turbine efficiency, that is durable, and resistant to flame holding and flash back. | 08-05-2010 |
| 20100263383 | GAS TURBINE PREMIXER WITH INTERNAL COOLING - A system that includes a turbine fuel nozzle comprising an air-fuel premixer. The air-fuel premixed includes a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises an internal coolant path from a downstream end portion in an upstream direction through a substantial length of the swirl vane. | 10-21-2010 |
| 20100280732 | METHOD FOR DETECTING GAS TURBINE ENGINE FLASHBACK - A method for monitoring and controlling a gas turbine, comprises predicting frequencies of combustion dynamics in a combustor using operating conditions of a gas turbine, receiving a signal from a sensor that is indicative of combustion dynamics in the combustor, and detecting a flashback if a frequency of the received signal does not correspond to the predicted frequencies. | 11-04-2010 |
| 20100326079 | METHOD AND SYSTEM TO REDUCE VANE SWIRL ANGLE IN A GAS TURBINE ENGINE - A fuel nozzle assembly includes a swirler assembly having an inlet end, an outlet end, a shroud inner surface and a hub outer surface. The inner surface has a first diameter adjacent to the inlet end and a second diameter adjacent to the outlet end defining a differential diameter ratio. A plurality of vanes are coupled to the swirler assembly and extend between the shroud inner surface and the hub outer surface. The vanes have a pair of opposing sidewalls joined at a leading edge and at an axially-spaced trailing edge, and a first height adjacent to the leading edge and a second height adjacent to the trailing edge. The first height and the second height define a differential height ratio, wherein the differential diameter ratio, the differential height ratio, or both are configured to provide convergent flow through the fuel nozzle. | 12-30-2010 |
| 20110000214 | METHODS AND SYSTEMS TO THERMALLY PROTECT FUEL NOZZLES IN COMBUSTION SYSTEMS - A method of assembling a gas turbine engine is provided. The method includes coupling a combustor in flow communication with a compressor such that the combustor receives at least some of the air discharged by the compressor. A fuel nozzle assembly is coupled to the combustor and includes at least one fuel nozzle that includes a plurality of interior surfaces, wherein a thermal barrier coating is applied across at least one of the plurality of interior surfaces to facilitate shielding the interior surfaces from combustion gases. | 01-06-2011 |
| 20110016871 | GAS TURBINE PREMIXING SYSTEMS - Methods and systems are provided for premixing combustion fuel and air within gas turbines. In one embodiment, a combustor includes an upstream mixing panel configured to direct compressed air and combustion fuel through a premixing zone to form a fuel-air mixture. The combustor also includes a downstream mixing panel configured to mix additional combustion fuel with the fuel-air mixture to form a combustion mixture. | 01-27-2011 |
| 20110072824 | APPARTUS AND METHOD FOR A GAS TURBINE NOZZLE - A nozzle includes an inlet, an outlet, and an axial centerline. A shroud surrounding the axial centerline extends from the inlet to the outlet and defines a circumference. The circumference proximate the inlet is greater than the circumference at a first point downstream of the inlet, and the circumference at the first point downstream of the inlet is less than the circumference at a second point downstream of the first point. A method for supplying a fuel through a nozzle directs a first airflow along a first path and a second airflow along a second path separate from the first path. The method further includes injecting the fuel into at least one of the first path or the second path and accelerating at least one of the first airflow or the second airflow. | 03-31-2011 |
